NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 50,000 Max Cl/Cd: 23.72 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20610-il-50000.txt Download as CSV file: xf-sc20610-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4943 0.09935 0.09161 -0.0008 1.0000 0.4003
-8.500 -0.6598 0.07155 0.06404 -0.0385 1.0000 0.1741
-8.250 -0.6718 0.06359 0.05576 -0.0429 1.0000 0.1579
-8.000 -0.6740 0.05609 0.04767 -0.0471 1.0000 0.1469
-7.750 -0.6603 0.05131 0.04231 -0.0489 1.0000 0.1441
-7.500 -0.6420 0.04696 0.03741 -0.0506 1.0000 0.1446
-7.250 -0.6196 0.04294 0.03286 -0.0521 1.0000 0.1457
-7.000 -0.5971 0.03958 0.02936 -0.0522 1.0000 0.1481
-6.750 -0.5730 0.03704 0.02662 -0.0524 1.0000 0.1547
-6.500 -0.5440 0.03434 0.02320 -0.0534 1.0000 0.1605
-6.250 -0.5209 0.03213 0.02109 -0.0528 1.0000 0.1691
-6.000 -0.4947 0.03011 0.01883 -0.0525 1.0000 0.1795
-5.750 -0.4694 0.02846 0.01701 -0.0518 1.0000 0.1926
-5.500 -0.4465 0.02698 0.01558 -0.0504 1.0000 0.2085
-5.250 -0.4253 0.02565 0.01446 -0.0484 1.0000 0.2289
-5.000 -0.4034 0.02432 0.01334 -0.0467 1.0000 0.2589
-4.750 -0.3805 0.02250 0.01215 -0.0458 1.0000 0.3208
-4.500 -0.3815 0.02170 0.01366 -0.0364 1.0000 0.5435
-4.250 -0.3846 0.02482 0.01669 -0.0238 1.0000 0.6856
-4.000 -0.3859 0.02644 0.01817 -0.0133 1.0000 0.7323
-3.750 -0.3829 0.02724 0.01884 -0.0051 1.0000 0.7727
-3.500 -0.3804 0.02743 0.01891 0.0032 1.0000 0.8076
-3.250 -0.3748 0.02715 0.01850 0.0101 1.0000 0.8445
-3.000 -0.3627 0.02643 0.01761 0.0157 1.0000 0.8836
-2.750 -0.1213 0.02470 0.01482 -0.0193 1.0000 0.9869
-2.500 -0.0667 0.02388 0.01381 -0.0262 1.0000 1.0000
-2.250 -0.0590 0.02352 0.01341 -0.0240 1.0000 1.0000
-2.000 -0.0517 0.02319 0.01306 -0.0217 1.0000 1.0000
-1.750 -0.0447 0.02289 0.01275 -0.0193 1.0000 1.0000
-1.500 -0.0380 0.02262 0.01247 -0.0168 1.0000 1.0000
-1.250 -0.0317 0.02237 0.01222 -0.0142 1.0000 1.0000
-1.000 -0.0256 0.02214 0.01199 -0.0116 1.0000 1.0000
-0.750 -0.0199 0.02192 0.01179 -0.0089 1.0000 1.0000
-0.500 -0.0143 0.02171 0.01160 -0.0062 1.0000 1.0000
-0.250 -0.0088 0.02151 0.01143 -0.0034 1.0000 1.0000
0.000 -0.0032 0.02132 0.01128 -0.0008 1.0000 1.0000
0.250 0.0028 0.02115 0.01115 0.0018 1.0000 1.0000
0.500 0.0108 0.02101 0.01106 0.0040 1.0000 1.0000
0.750 0.0240 0.02097 0.01107 0.0051 1.0000 1.0000
1.000 0.0422 0.02104 0.01119 0.0054 1.0000 1.0000
1.250 0.0640 0.02120 0.01144 0.0049 1.0000 1.0000
1.500 0.0884 0.02146 0.01178 0.0040 1.0000 1.0000
1.750 0.1144 0.02179 0.01223 0.0027 1.0000 1.0000
2.000 0.1414 0.02221 0.01278 0.0011 1.0000 1.0000
2.250 0.1691 0.02271 0.01344 -0.0006 1.0000 1.0000
2.500 0.1969 0.02330 0.01420 -0.0025 1.0000 1.0000
2.750 0.2247 0.02399 0.01509 -0.0045 1.0000 1.0000
3.000 0.2521 0.02479 0.01614 -0.0067 1.0000 1.0000
3.250 0.2820 0.02577 0.01739 -0.0096 0.9977 1.0000
3.500 0.4566 0.02374 0.01636 -0.0291 0.8778 1.0000
3.750 0.5433 0.02290 0.01251 -0.0249 0.2978 1.0000
4.000 0.5798 0.02487 0.01407 -0.0263 0.2412 1.0000
4.250 0.6190 0.02672 0.01575 -0.0281 0.2099 1.0000
4.500 0.6553 0.02870 0.01765 -0.0295 0.1905 1.0000
4.750 0.6878 0.03070 0.01974 -0.0304 0.1755 1.0000
5.000 0.7186 0.03295 0.02233 -0.0309 0.1652 1.0000
5.250 0.7484 0.03551 0.02500 -0.0316 0.1563 1.0000
5.500 0.7754 0.03822 0.02831 -0.0315 0.1509 1.0000
5.750 0.8030 0.04101 0.03116 -0.0321 0.1440 1.0000
6.000 0.8274 0.04478 0.03530 -0.0322 0.1424 1.0000
6.250 0.8476 0.04850 0.03962 -0.0318 0.1419 1.0000
6.500 0.8644 0.05250 0.04419 -0.0313 0.1415 1.0000
6.750 0.8821 0.05708 0.04914 -0.0314 0.1423 1.0000
7.000 0.8812 0.06333 0.05641 -0.0307 0.1549 1.0000
7.250 0.8902 0.07072 0.06421 -0.0319 0.1725 1.0000
7.500 0.7744 0.06797 0.06234 -0.0201 0.1898 1.0000
7.750 0.7198 0.10618 0.10063 -0.0755 0.4054 1.0000
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Polar data table (+)
Polar graphs
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